JPS632776Y2 - - Google Patents
Info
- Publication number
- JPS632776Y2 JPS632776Y2 JP1982166916U JP16691682U JPS632776Y2 JP S632776 Y2 JPS632776 Y2 JP S632776Y2 JP 1982166916 U JP1982166916 U JP 1982166916U JP 16691682 U JP16691682 U JP 16691682U JP S632776 Y2 JPS632776 Y2 JP S632776Y2
- Authority
- JP
- Japan
- Prior art keywords
- pressure
- pilot burner
- air
- gas
- pilot
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
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- Gas Burners (AREA)
- Feeding And Controlling Fuel (AREA)
Description
【考案の詳細な説明】
本考案はガス燃焼装置におけるパイロツトバー
ナの改良に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an improvement of a pilot burner in a gas combustion device.
一般に、燃焼装置におけるバーナへの点火方法
として、比較的着火性の低い燃料（例えば重質油
燃料）又は大容量の燃料については、燃焼装置に
ガス燃料によるパイロツトバーナを装着している
ものが多い。 Generally, as a method of igniting the burner in a combustion device, for fuels with relatively low ignitability (e.g. heavy oil fuel) or large capacity fuels, the combustion device is often equipped with a pilot burner using gas fuel. .
第１図は通常用いられているパイロツトバーナ
を有する燃焼装置の配管図である。図において、
１は燃焼器、２は主燃バーナ、３はパイロツト燃
焼室、４はパイロツトバーナノズル、５は混合
器、６はゼロガバナ、７は減圧弁、８は空気供給
管、９はガス供給管、１０は二次圧検出器、１１
は主燃焼器出口であり、主燃バーナ２に空気とガ
スが供給され、燃焼器１で燃焼した燃焼ガスは主
燃焼器出口１１から排出される。一方、空気供給
管８に空気が、ガス供給管９にガスがそれぞれ供
給され、両者は混合器５で一定比率に混合されて
パイロツトバーナノズル４に供給され、パイロツ
ト燃焼室３でパイロツトガスに炎が形成され、主
燃バーナ２の着火を助勢する。ここで混合器５で
混合された空気とガスの二次圧（燃焼内圧）を検
出する検出器１０によつてガス供給管９に設けら
れたパイロツトバーナ燃料ガスの供給弁であるゼ
ロガバナ６を調整し点火を調整している。 FIG. 1 is a piping diagram of a commonly used combustion apparatus having a pilot burner. In the figure,
1 is a combustor, 2 is a main combustion burner, 3 is a pilot combustion chamber, 4 is a pilot burner nozzle, 5 is a mixer, 6 is a zero governor, 7 is a pressure reducing valve, 8 is an air supply pipe, 9 is a gas supply pipe, 10 is a secondary pressure detector, 11
is a main combustor outlet, air and gas are supplied to the main combustion burner 2, and combustion gas combusted in the combustor 1 is discharged from the main combustor outlet 11. On the other hand, air is supplied to the air supply pipe 8 and gas is supplied to the gas supply pipe 9, and both are mixed at a constant ratio in the mixer 5 and supplied to the pilot burner nozzle 4, where the pilot gas is ignited into flame in the pilot combustion chamber 3. is formed to assist the ignition of the main combustion burner 2. Here, a zero governor 6, which is a pilot burner fuel gas supply valve provided in a gas supply pipe 9, is adjusted by a detector 10 that detects the secondary pressure (combustion internal pressure) of the air and gas mixed in the mixer 5. and adjusting the ignition.
そして、主燃焼器１から高温高圧の燃焼ガスを
供給する燃焼装置においては、パイロツトバーナ
から主燃料へ点火する過程で、主燃焼器内の圧力
が瞬時に上昇するため、パイロツトバーナ燃料ガ
スの供給用弁であるゼロガバナ６の作動（追従性
能）が問題となり、ゼロガバナの追従が悪いとミ
ス着火を誘発することが多い。 In a combustion device that supplies high-temperature, high-pressure combustion gas from the main combustor 1, the pressure inside the main combustor increases instantaneously during the process of igniting the main fuel from the pilot burner. The operation (following performance) of the zero governor 6, which is a control valve, becomes a problem, and poor tracking of the zero governor often leads to mis-ignition.
特に、燃焼器後部（出口）の絞り比が大きい燃
焼装置に対して上記ミス着火という現象は避け難
く、一方、追従性能の高い供給弁（ゼロガバナ）
は機能が複雑となり、非常に高価になるばかりで
なく、着火条件が限定される。 In particular, the above-mentioned phenomenon of mis-ignition is difficult to avoid for combustion equipment with a large throttle ratio at the rear (outlet) of the combustor.
Not only is the function complicated and very expensive, but the ignition conditions are limited.
本考案は上記のような従来の不具合を解消する
ことを目的とした非常に構造簡単なパイロツトバ
ーナを提供するものである。 The present invention aims to solve the above-mentioned conventional problems and provides a pilot burner with a very simple structure.
上記目的は、パイロツトバーナにおいて、燃料
（ガス）供給系、および空気等の燃料酸化剤供給
系にそれぞれ多段減圧オリフイスを設け、混合器
に流入する燃料／酸化剤の混合比が常に一定で二
次圧（燃焼器内圧）の影響を受けないようにした
ことによつて達成される。 The above purpose is to provide multistage decompression orifices in the fuel (gas) supply system and the fuel oxidizer supply system such as air in the pilot burner, so that the mixture ratio of fuel/oxidant flowing into the mixer is always constant and secondary. This is achieved by not being affected by pressure (combustor internal pressure).
本考案はガスタービン、MHD発電、高圧ガス
バーナ、ボイラおよび加熱炉等の燃焼装置に広く
応用できる。 The present invention can be widely applied to combustion equipment such as gas turbines, MHD power generation, high-pressure gas burners, boilers, and heating furnaces.
以下、本考案の実施例を図面と共に説明する。 Embodiments of the present invention will be described below with reference to the drawings.
第２図は本考案によるパイロツトバーナを有す
る燃焼装置を示したものであり、第３図は各器内
の圧力変動を示した特性図である。 FIG. 2 shows a combustion apparatus having a pilot burner according to the present invention, and FIG. 3 is a characteristic diagram showing pressure fluctuations in each vessel.
第２図に示す本考案のパイロツトバーナは主燃
焼室１ａの上流に取り付けられ、パイロツトバー
ナ燃焼室３ａ、パイロツトバーナノズル４ａ、混
合器５ａ、空気多段減圧器１２、燃料ガスタ段減
圧器１５及び空気供給管８ａ、燃料ガス供給管９
ａをそれぞれ接続して構成する。なお２ａは主燃
バーナである。 The pilot burner of the present invention shown in FIG. 2 is installed upstream of the main combustion chamber 1a, and includes a pilot burner combustion chamber 3a, a pilot burner nozzle 4a, a mixer 5a, an air multistage pressure reducer 12, a fuel gas star pressure reducer 15, and an air Supply pipe 8a, fuel gas supply pipe 9
a are connected to each other. Note that 2a is a main combustion burner.
ここで本考案による構成要件である気体通路を
構成する円板状の空気多段減圧オリフイス１３が
空気多段減圧器１２内に、また、燃料ガスの多段
減圧オリフイス１６がガス多段減圧器１５内にそ
れぞれ３〜４枚挿入されている。前記円板オリフ
イス１３，１６にはそれぞれ空気孔１４及びガス
孔１７が千鳥状になるように配列されている。ま
た、混合器５ａは燃料ガス噴口と空気供給用エゼ
クタ（図示せず）を内装している。一方、パイロ
ツトバーナノズル４ａは噴出速度80〜100m／秒
の高速バーナを備えている。 Here, a disc-shaped multi-stage air pressure reducing orifice 13 constituting a gas passage, which is a component according to the present invention, is located in the air multi-stage pressure reducer 12, and a fuel gas multi-stage pressure reducing orifice 16 is located in the gas multi-stage pressure reducer 15. 3 to 4 sheets are inserted. Air holes 14 and gas holes 17 are arranged in a staggered manner in each of the disk orifices 13 and 16. The mixer 5a also includes a fuel gas nozzle and an air supply ejector (not shown). On the other hand, the pilot burner nozzle 4a is equipped with a high-speed burner with an ejection speed of 80 to 100 m/sec.
上記構成についてその作用を説明すれば、先
づ、混合器５ａに供給される燃料ガスと空気はそ
れぞれの空気多段減圧器１２、ガス多段減圧器１
５に内挿している減圧オリフイス１３，１６の組
合せによつて所定の流量比率で流入するように設
定されている。また燃料ガスおよび空気の供給圧
力はそれぞれの多段減圧オリフイス１３，１６の
絞りに対し臨界圧以上に設定されている。そし
て、第２図および第３図に示すように、主燃焼室
圧力P3は点火過程で瞬間的な変動を生じる。こ
の圧力変動に対して、パイロツトバーナ系の圧力
である混合器５ａの出口圧力P1、パイロツトバ
ーナ燃焼室３内圧力P2は十分に高く、更に、混
合器５ａへ供給される燃料ガスは出口圧力P0の
多段減圧器１５を介することによつて混合器二次
圧P1の変動に影響なく一定のガス流量が保たれ
る。 To explain the operation of the above configuration, first, the fuel gas and air supplied to the mixer 5a are supplied to the air multi-stage pressure reducer 12 and the gas multi-stage pressure reducer 1.
A combination of depressurizing orifices 13 and 16 inserted in 5 is set to flow in at a predetermined flow rate. Further, the supply pressures of the fuel gas and air are set to be higher than the critical pressure for each of the multi-stage decompression orifices 13 and 16. As shown in FIGS. 2 and 3, the main combustion chamber pressure P 3 undergoes instantaneous fluctuations during the ignition process. Against this pressure fluctuation, the outlet pressure P 1 of the mixer 5a, which is the pressure of the pilot burner system, and the pressure P 2 inside the pilot burner combustion chamber 3 are sufficiently high, and furthermore, the fuel gas supplied to the mixer 5a is By passing through the multi-stage pressure reducer 15 at the pressure P 0 , a constant gas flow rate is maintained without being affected by fluctuations in the mixer secondary pressure P 1 .
以上述べてきたように、本考案は、第１図に示
す従来の調圧弁（ゼロガバナ）、減圧弁に比べて
多段減圧器を用いたので製品コストが半減され
る。また、パイロツトバーナとして高圧燃焼器へ
の適応性が高く、着火ミスがないのでプラントの
信頼性向上につながる等極めて優れた実用的効果
を奏することができる。 As described above, the present invention uses a multi-stage pressure reducer compared to the conventional pressure regulating valve (zero governor) and pressure reducing valve shown in FIG. 1, so the product cost is halved. In addition, it is highly adaptable to high-pressure combustors as a pilot burner, and since there is no ignition error, it can produce extremely excellent practical effects such as improving the reliability of the plant.
第１図は従来用いられているパイロツトバーナ
を有する燃焼装置の配管図、第２図は本考案の一
実施例によるパイロツトバーナを有する燃焼装置
の配管図、第３図は本考案の各器内圧力変動を示
す特性図である。
１ａ……主燃焼室、２ａ……主燃バーナ、３ａ
……パイロツトバーナ燃焼室、４ａ……パイロツ
トバーナノズル、５ａ……混合器、８ａ……空気
供給管、９ａ……燃料ガス供給管、１１ａ主燃焼
器出口、１２……空気多段減圧器、１３……同多
段オリフイス、１４……空気孔、１５……ガス多
段減圧器、１６……同多段オリフイス、１７……
ガス孔、P0……ガス多段減圧器出口圧力、P1…
…混合器出口圧力、P2……パイロツトバーナ燃
焼室圧力、P3……主燃焼器内圧力。
Fig. 1 is a piping diagram of a combustion device with a conventionally used pilot burner, Fig. 2 is a piping diagram of a combustion device with a pilot burner according to an embodiment of the present invention, and Fig. 3 is a piping diagram of a combustion device with a pilot burner according to an embodiment of the present invention. FIG. 3 is a characteristic diagram showing pressure fluctuations. 1a... Main combustion chamber, 2a... Main combustion burner, 3a
... Pilot burner combustion chamber, 4a ... Pilot burner nozzle, 5a ... Mixer, 8a ... Air supply pipe, 9a ... Fuel gas supply pipe, 11a Main combustor outlet, 12 ... Air multistage pressure reducer, 13 ...Same multi-stage orifice, 14...Air hole, 15...Gas multi-stage pressure reducer, 16...Same multi-stage orifice, 17...
Gas hole, P 0 ... Gas multistage pressure reducer outlet pressure, P 1 ...
... Mixer outlet pressure, P 2 ... Pilot burner combustion chamber pressure, P 3 ... Main combustor internal pressure.
Claims (1)
置され、パイロツト燃焼室、パイロツトバーナノ
ズル、混合器、空気供給管、および燃料ガス供給
管より構成されたパイロツトバーナにおいて、空
気および燃料ガス供給系にそれぞれ多段減圧オリ
フイスを組み込むと共に、前記空気および燃料ガ
ス供給系におけるそれぞれの供給圧を前記主燃焼
室内の瞬時的圧力変動に対して高圧に設定したこ
とを特徴とするパイロツトバーナ。 The air and fuel gas supply system is installed in the pilot burner, which is installed upstream of the main combustion chamber that uses fuel with low ignitability, and is composed of a pilot combustion chamber, a pilot burner nozzle, a mixer, an air supply pipe, and a fuel gas supply pipe. A pilot burner characterized in that a multi-stage pressure reducing orifice is incorporated in each of the pilot burners, and the respective supply pressures in the air and fuel gas supply systems are set at high pressures with respect to instantaneous pressure fluctuations in the main combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16691682U JPS5971039U (en) | 1982-11-05 | 1982-11-05 | pilot burner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16691682U JPS5971039U (en) | 1982-11-05 | 1982-11-05 | pilot burner |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5971039U JPS5971039U (en) | 1984-05-14 |
| JPS632776Y2 true JPS632776Y2 (en) | 1988-01-23 |
Family
ID=30365304
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP16691682U Granted JPS5971039U (en) | 1982-11-05 | 1982-11-05 | pilot burner |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5971039U (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6488550B2 (en) * | 2014-03-27 | 2019-03-27 | 三浦工業株式会社 | boiler |
| JP7126685B2 (en) * | 2018-05-24 | 2022-08-29 | 株式会社パロマ | Combustion device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5125840A (en) * | 1974-08-29 | 1976-03-03 | Mitsubishi Heavy Ind Ltd | GASUBAANA |
| JPS5417425U (en) * | 1977-07-07 | 1979-02-03 |
-
1982
- 1982-11-05 JP JP16691682U patent/JPS5971039U/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5971039U (en) | 1984-05-14 |
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